EP3133418A1 - Structure d'assemblage - Google Patents

Structure d'assemblage Download PDF

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Publication number
EP3133418A1
EP3133418A1 EP16184533.4A EP16184533A EP3133418A1 EP 3133418 A1 EP3133418 A1 EP 3133418A1 EP 16184533 A EP16184533 A EP 16184533A EP 3133418 A1 EP3133418 A1 EP 3133418A1
Authority
EP
European Patent Office
Prior art keywords
axis
shroud
mounting structure
aircraft
base
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP16184533.4A
Other languages
German (de)
English (en)
Inventor
Gregor WHITE
Eric Philip SCHOESSOW
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
BAE Systems PLC
Original Assignee
BAE Systems PLC
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by BAE Systems PLC filed Critical BAE Systems PLC
Publication of EP3133418A1 publication Critical patent/EP3133418A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S7/00—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00
    • G01S7/02—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00 of systems according to group G01S13/00
    • G01S7/41—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00 of systems according to group G01S13/00 using analysis of echo signal for target characterisation; Target signature; Target cross-section
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S7/00—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00
    • G01S7/02—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00 of systems according to group G01S13/00
    • G01S7/40—Means for monitoring or calibrating
    • G01S7/4004—Means for monitoring or calibrating of parts of a radar system

Definitions

  • the present invention relates to mounting structures for supporting objects, for example, but not limited to, during radar cross section measurements of the objects.
  • Aircraft radar cross section tends to be an important parameter in the field of military aircraft design.
  • the radar cross section of an aircraft is measured or predicted by placing the aircraft, or test model representative of the aircraft, in an anechoic chamber or outdoor test range, illuminating the aircraft/model with a radar signal, and measuring the radar return from the aircraft model.
  • the aircraft or model is generally supported in the anechoic chamber or outdoor test range by one or more upwardly extending supports or "pylons", for example, an ogive pylon.
  • the supports should have a substantially lower radar cross section than the test aircraft or model.
  • the present invention provides a mounting structure for supporting an object during a radar cross section measurement of the object.
  • the mounting structure comprises: a base configured to rotate about a first axis; an elongate support extending upwardly from the base to a tip, the tip being configured to receive the object; and a shroud housing at least a portion of the elongate support.
  • the shroud is configured to rotate about a second axis, the second axis being substantially parallel to the first axis, the rotation of the shroud about the second axis being in a direction that is opposite to the rotation of the base about the first axis.
  • a rotational speed of the base about the first axis may be substantially equal to a rotational speed of the shroud about the second axis.
  • the object may be an object selected from the group of objects consisting of an aircraft and a test model of an aircraft.
  • the base may be configured to rotate substantially parallel to a ground plane.
  • the first axis may be substantially perpendicular to the ground plane.
  • the mounting structure may be for supporting the object above the ground plane.
  • the shroud may be at least partially coated in or formed from a radar absorbent material.
  • a cross section of the shroud may comprise a tapered portion.
  • the shroud may have a tear-drop shaped cross section.
  • the mounting structure may further comprise one or more further elongate supports extending upwardly from the base to a further tip.
  • the further supports may be parallel to the support.
  • the further supports and the support may extend from the base in a common direction.
  • the one or more further tips may be configured to receive the object.
  • the mounting structure may further comprise one or more further shrouds, each of the further shrouds housing at least a portion of a respective further elongate support.
  • Each further shroud may be configured to rotate about a respective further axis, each further axis being substantially parallel to the first axis, the rotation of each further shroud being in a direction that is opposite to the rotation of the base about the first axis.
  • a cross section of the shroud may comprise a tapered portion.
  • a cross section of each further shroud may comprise a tapered portion.
  • the shroud and each of the further shrouds may be oriented such that all of the tapered portions point to a common point remote from the mounting structure and/or in a common direction.
  • the present invention provides a system for measuring a radar cross section of an object.
  • the system comprises a mounting structure according to any of the preceding aspects, and one or more radar antennas remote from the mounting structure and arranged to transmit radio waves towards the mounting structure.
  • the shroud and each of the further shrouds may be oriented such that all of the tapered portions point to the one or more radar antennas.
  • the system may further comprise a frame having a first end and a second end.
  • the frame may be attached to a ground plane at or proximate to the first end.
  • the frame may extend upwardly from the ground plane to the second end.
  • the system may further comprise a measurement module coupled to the frame, the measurement module comprising the one or more radar antennas.
  • the measurement module may be moveable along the frame between the first end and the second end.
  • the measurement module may be configured to rotate about an axis such that the orientation of the measurement module with respect to the frame may be changed.
  • the mounting structure may be located in a near field region of the one or more antennas.
  • the present invention comprises a method of supporting an object during a radar cross section measurement of the object.
  • the method comprises: providing a base configured to rotate about a first axis; providing an elongate support extending upwardly from the base to a tip; housing at least a portion of the elongate support within a shroud, wherein the shroud is configured to rotate about a second axis, the second axis being substantially parallel to the first axis, the rotation of the shroud being in a direction that is opposite to the rotation of the base about the first axis; and fixing the object to the tip.
  • the method may further comprise rotating the base in a first direction about the first axis, and rotating the shroud in a second direction about the second axis, wherein the second direction is opposite to the first direction.
  • Figure 1 is a schematic illustration (not to scale) of showing a system 100 in which a radar cross section of an aircraft 102 is measured.
  • the system 100 comprises an aircraft mounting structure 104 on which the aircraft 102 is mounted, and a radar cross section measurement apparatus 106.
  • the aircraft mounting structure 104 comprises a turntable 108, three shrouds 110, and three supporting members 112.
  • the turntable 108 is cylindrical in shape.
  • Figure 1 shows a side view of the aircraft mounting structure 104, and thus the turntable 108 appears rectangular.
  • the turntable 108 is recessed or sunk into the ground 113 such that an upper surface of the turntable 108 is substantially parallel with the surface of the ground 113.
  • each of the shrouds 110 is a cover or housing for a respective supporting member 112. External surfaces of the shrouds 110 may be covered in a radar absorbent material (RAM). Further details of the shrouds 110 and the supporting members 112 housed therein are provided later below with reference to Figure 4 .
  • RAM radar absorbent material
  • the supporting members 112 are substantially perpendicular to the upper surface of the turntable 108. A first end of each of the supporting members 112 is attached to the upper surface of the turntable 108. A second end of each of the supporting members 112 (a second end of a supporting member 112 being an opposite end to the first end of the supporting member 112) is attached to a respective hardpoint of the aircraft 102.
  • the aircraft 102 is held above the turntable 108, by the supporting members 112 (which are housed in respective shrouds 110), in a fixed position relative to the turntable 108.
  • the turntable 108 rotates about its axis, thereby causing rotation of the aircraft 102 relative to the measurement apparatus 106.
  • the external surfaces of the shrouds 110 are coated with a radar absorbent material (RAM). Also, at least the upper surface of the turntable 108 is coated with a RAM.
  • RAM radar absorbent material
  • electrical wires and/or hydraulic lines may run within the shrouds 110.
  • the aircraft 102 may be supplied with power, data, etc. during measurement of its radar cross section.
  • the measurement apparatus 106 is spatially separated from the aircraft mounting structure 104 and the aircraft 102 by a predetermined distance, for example 19m.
  • the measurement apparatus 106 comprises a frame 114 and a radar cross section measurement module 116.
  • the measurement apparatus 106 and its operation will be described in more detail later below with reference to Figures 5 to 7 .
  • the measurement apparatus 106 comprises a frame 114 and a radar cross section measurement module 116.
  • the frame 114 is fixed at a first end to the ground 113, and extends substantially vertically from the ground 113.
  • the height of a second end of the frame 114 (the second end of the frame 114 being a distal end of the frame 114 opposite to the first end of the frame 114) above the ground 113 is approximately 12m.
  • the frame 114 is fixed to the ground either side of a cavity 117 recessed into the ground 113.
  • the measurement module 116 is slidably mounted to the frame 114, and may be moved along the length of the frame 114.
  • the height of the measurement module 116 above the ground 113 may be altered.
  • the measurement module 116 may be moved along the frame 114 to be at or proximate to the first end of the frame 114 such that measurement module 116 is at least partially within the cavity 117.
  • the measurement module 116 emits radio waves 118, from the measurement apparatus 106, in the direction of the aircraft mounting structure 104 and the aircraft 102, as indicated in Figure 1 by dotted arrows.
  • the radio waves 118 incident on the aircraft mounting structure 104 and the aircraft 102 may be reflected by the aircraft mounting structure 104 and/or the aircraft 102 back towards the measurement module 116.
  • the measurement module 116 is further configured to detect radio waves 118 that have been reflected by the aircraft mounting structure 104 and/or the aircraft 102 towards the measurement module 116.
  • Figure 2 is a schematic illustration (not to scale) showing a perspective view of the aircraft mounting structure 104.
  • Figure 3 is a schematic illustration (not to scale) showing a plan view of the aircraft mounting structure 104.
  • the turntable 108 is configured to be rotated about its axis by one or more motors (not shown in the Figures).
  • the upper surface of the turntable 108 rotates about its centre point 200 as indicates in Figures 2 and 3 by double-headed solid arrows.
  • Rotation of the turntable is controlled by a computer (not shown in the Figures).
  • each shroud 110 is substantially that of a conical frustum having a tear-drop shaped base with a cut-out portion 204.
  • the cut-out portion 204 is located at the tapered portion of the largest base of the conical frustum.
  • each shroud 110 is substantially that of a portion of a cone having a tear-shaped base that lies between two parallel planes cutting that cone, and includes a cut-out portion 204 located at the tip (i.e. point or vertex) of the (tear-drop shaped) largest base of the conical frustum.
  • the upper portion of each shroud 110 is a cylindrical sleeve covering the upper portion of a respective supporting member 112. This upper portion is covered by a RAM component.
  • This RAM component is cylindrical in shape and has a tear-shaped cross-section. This RAM component aligned with the shroud lower portion.
  • each shroud 110 comprises a "front edge" 206 that extends from the tip (i.e. point or vertex) of the tear-drop shaped smallest base of the conical frustum shape of that shroud 110 to the cut-out portion 204 of that shroud 110.
  • each shroud 110 the largest of the bases of its conical frustum shape is proximate to the turntable 108.
  • each of the shrouds 110 counter rotates (for example, in an anti-clockwise direction) about its respective axis relative to the turntable 108.
  • the counter rotation of the shrouds 110 is at the same rotational speed as the rotation of the turntable 108. This matching of the rotational speed of the turntable 108 and the rotational speeds of the shrouds 110 advantageously tends to provide that, as the turntable 108 rotates about its axis, the shrouds 110 maintain the same orientation with respect to entities remote from the turntable 108, for example the measurement apparatus 106.
  • the shrouds 110 are positioned on the turntable 108 such that the front edges 206 of the shrouds 110 face the measurement apparatus 106.
  • a point on the front edge 206 of each shrouds 110 may be the closest point on that shroud 110 to the measurement apparatus 106.
  • a line that passes from the axis of that shroud assembly 110 through the front edge 206 of that shroud 110 points towards the measurement apparatus 106.
  • a line that passes from the axis of that shroud assembly 110 and bisects the angle between the sides of that shroud 110 at the front edge 206 of that shroud 110 points towards the measurement apparatus 106.
  • the rotational speed of the turntable 108 and the counter rotational speeds of the shrouds 110 advantageously tends to provide that, as the turntable 108 rotates about its axis, the front edges 206 of the shrouds 110 face the measurement apparatus 106.
  • the cut-out portions 204 tends to allow the shrouds 110 to move past each other as the turntable 108 rotates and the shrouds 110 counter-rotate.
  • FIG 4 is a schematic illustration (not to scale) showing apparatus housed within a shroud 110.
  • the shroud 110 housing the apparatus has been partially removed.
  • the apparatus within the shroud 110 comprises a tripod 400, a cylindrical member 401, a ring gear 402, and a motor 404, a plurality of horizontal rollers 406.
  • the tripod 400 is the base portion of a supporting member 112. A base of the tripod 400 is fixedly attached to the turntable 108 such that the position and orientation of the tripod 400 relative to the turntable 108 is fixed.
  • the tripod 400 is further fixedly attached to a cylindrical member 410 such that the position and orientation of the tripod 400 relative to the cylindrical member 401 is fixed.
  • the cylindrical member 401 is the upper portion of a supporting member 112.
  • the cylindrical member 401 passes through the apex of the tripod 400 (i.e. the end of the tripod 400 that is opposite to the base of the tripod 400).
  • the tripod 400 advantageously tends to maintain the stability of the cylindrical member 401 and the aircraft 102 mounted thereon as the turntable 108 rotates about its axis.
  • the ring gear 402 is located at the apex of the tripod 400.
  • the ring gear 402 fits around the cylindrical member 401, i.e. the cylindrical member 401 passes through the ring gear 402.
  • the ring gear 402 is coaxial with the cylindrical member 401.
  • the motor 404 is coupled to the ring gear 402 and is configured to rotate the ring gear 402 about the axis of the ring gear 402 (i.e. about the axis of the cylindrical member 401).
  • the motor 404 is coupled to a drive system of the turntable 108 and is configured to, as the turntable 108 is rotated about the axis of the turntable 108, counter rotate the ring gear 402 about the axis of the ring gear 402.
  • the ring gear 402 is counter rotated at the same rotational speed as the turntable 108, albeit in the opposite direction.
  • the shroud 110 is fixedly attached to the ring gear 402 such that the position and orientation of the shroud 110 relative to the ring gear 402 is fixed.
  • the motor 404 rotates the shroud 110 (by rotating the ring gear 402) about the axis of the cylindrical member 401.
  • the shroud 110 is rotated around the tripod 400.
  • This rotation of the shroud 110 around the tripod 400 is facilitated by the horizontal rollers 406 that are mounted to the tripod 400 at or proximate to the base of the tripod 400.
  • Figure 5 is a schematic illustration (not to scale) showing a side view of the measurement apparatus 106.
  • Figure 6 is a schematic illustration (not to scale) showing a plan view of the measurement apparatus 106.
  • the frame 114 comprises a plurality of steel beams that are attached together by, for example, welding or bolts.
  • the frame 114 is advantageously resistant to deflection, for example, as a result of wind.
  • the frame 114 comprises two vertical spaced apart towers 114a.
  • the two towers 114a are coupled together via two rear braces 114b.
  • the towers 114a are positioned either side of the cavity 117.
  • the height of each tower 114a above the ground 113 is approximately 12m.
  • each tower 114 is coupled to the ground 113 via mounting brackets including, for each tower 114, a first mounting bracket 500 and a second mounting bracket 502.
  • the measurement module 116 is mounted between the two towers 114a such that the measurement module 116 may be slid between different positions along the lengths of the two towers 114a. Also, in this embodiment, the measurement module 116 is mounted between the two towers 114a such that the orientation of the measurement module 116 with respect to the towers 114a may be changed.
  • movement of the measurement module 116 with respect to the frame 114 is driven by motors located at the first mounting brackets 500 and the second mounting brackets 502.
  • motors located at the first mounting brackets 500 control the angle or orientation of the measurement module 116 with respect to the frame 114.
  • the angle or orientation of the measurement module 116 is controlled by the differential rotation of motors located at the mounting brackets 500, 502.
  • motors located at the second mounting brackets 502 control the position of the measurement module 116 along the lengths of the towers 114a, i.e. the height of the measurement module 116 above the ground 113.
  • the height of the measurement module 116 is controlled by the common mode rotation of motors located at the mounting brackets 500, 502.
  • Positional and angular information of the measurement module 116 may be relayed, via the first and second mounting brackets 500, 502, to the computer.
  • the computer may include a controller for controlling the position and orientation of the measurement module with respect to the frame 114.
  • the measurement module 116 is located proximate to the top of the frame 114 (i.e. near to the distal ends of the towers 114a) and is inclined downwards such that the measurement module 116 is directed towards the aircraft 102.
  • the measurement module 116 is located substantially equidistant between the top and the bottom of the frame 114 (i.e. half-way along the lengths of the towers 114a) and is substantially horizontal such that the measurement module 116 is directed towards the aircraft 102.
  • the measurement module 116 is located proximate to the bottom of the frame 114 (i.e. near to the proximal ends of the towers 114a) and is inclined upwards such that the measurement module 116 is directed towards the aircraft 102.
  • the measurement module 116 is at least partially located within the cavity 117.
  • the cavity 117 allows for tilting of the measurement module 116 when the measurement module 116 is located proximate to the bottom of the frame 114.
  • the measurement module 116 comprises four radar antennas (which are herein after collectively referred to as the "antennas" and are collectively indicated in the Figures by the reference numeral 510), and a housing 512.
  • the antennas 510 are located within the housing 510, proximate to a rear end of the housing 512.
  • the antennas 510 are directed towards an opening located at a front end of the housing 512, the front end of the housing 512 being opposite to the rear end of the housing 512.
  • the antennas 510 transmit radio waves 118 from the rear end of the housing 512, to the front end of the housing 512, out of the opening of the housing 512, and onto the aircraft 102.
  • the antennas 510 receive radio waves reflected by the aircraft 102, and send electrical signals corresponding to the received radio waves to the computer.
  • the antennas 510 are mounted to a rotatable turntable operable to select of applicable antennas for measurement. In some embodiments, this turntable allows for the direction of the radio waves transmitted by the antennas 510 with respect to the housing 512 to be changed.
  • one or more further modules may be mounted within or onto the housing 512 in addition to the antennas 510.
  • Example further modules include, but are not limited to, power supply units, Radio Frequency (RF) convertors, and transceivers.
  • RF Radio Frequency
  • one or more of the further modules are mounted to a rack that may be removed from the housing 512, for example, by sliding the rack from the rear of the measurement modules 116 so as to allow access to the antennas 510.
  • the housing 512 is substantially rectangular cuboidal in shape.
  • a length of the housing 512 from the front end of the housing 512 to the rear end of the housing 512 is 3.54m.
  • a distance between the front end of the housing 512 and a transmitting face of the antennas 510 is 2.50m.
  • a height of the housing 512 from and upper surface of the housing 512 to a lower surface of the housing 512 is 1.60m.
  • a width of the housing 512 is 2.80m.
  • the walls of the housing 512 define the housing opening at the front end of the housing 512.
  • the walls of the housing 512 advantageously tend to reduce or eliminate the antenna 510 receiving radar returns from entities other than the aircraft 102. This advantageously tends to increase the accuracy with which the radar cross section of the aircraft 102 is determined.
  • the walls of the housing 512 advantageously form an aperture which directs emitted radio waves in only a desired direction.
  • the walls may be coated in RAM to enhance this effect and prevent internal reflections from corrupting the measurements.
  • the walls of the housing 512 are made from other materials instead of or in addition to CFC.
  • the walls may be made of aluminium panels that are approximately 3mm thick.
  • the housing 512 comprises one or more strengthening members or beams to reinforce the housing 512, for example, against wind loadings.
  • Apparatus including the computer, for implementing the above arrangement, and performing the method steps to be described later below, may be provided by configuring or adapting any suitable apparatus, for example one or more computers or other processing apparatus or processors, and/or providing additional modules.
  • the apparatus may comprise a computer, a network of computers, or one or more processors, for implementing instructions and using data, including instructions and data in the form of a computer program or plurality of computer programs stored in or on a machine readable storage medium such as computer memory, a computer disk, ROM, PROM etc., or any combination of these or other storage media.
  • Figure 7 is a process flow chart showing certain steps of an embodiment of a process of measuring a radar cross section of the aircraft 102.
  • the aircraft 102 is mounted to the aircraft mounting structure 104 as described in more detail earlier above with reference to Figure 1 .
  • the measurement module 116 is positioned and oriented on the frame 114 in a desired position. For example, in a first iteration of step s4 the measurement module 116 is located in the first position and orientation 504. Positioning and orienting the measurement module 116 on the frame may be performed by the computer controlling the motors of the first and second mounting brackets 500, 502.
  • the turntable 108 is rotated so as to position the aircraft 102 at a desired orientation with respect to the measurement module 116.
  • the motors 404 housed in the shrouds 110 counter rotate the shrouds 110 about the axes of the cylindrical portions 112.
  • the facings of the external skins 410 relative to the measurement apparatus 106 are maintained, i.e. the front edges 206 of the shrouds 410 remain directed towards the measurement apparatus 106 throughout rotation of the turntable 108.
  • the computer controls the measurement module 116 such that the antennas 510 transmit radio waves 118 onto the aircraft 102 and the aircraft mounting structure 104.
  • the antennas 510 receive radio waves reflected by the aircraft 102 and the aircraft mounting structure 104. An electrical signal corresponding to the reflected electromagnetic radiation received by the antennas 510 is sent to the computer.
  • the aircraft mounting structure 104 i.e. the turntable 108, the shrouds 110, and the cylindrical portions 112, are coated in RAM.
  • the aircraft mounting structure 104 i.e. the turntable 108, the shrouds 110, and the cylindrical portions 112
  • RAM the random access memory
  • the orientations of the shrouds 110 relative to the measurement module 116 advantageously tend to provide that the radar cross sections of the shrouds 110 are minimised.
  • the counter rotation of the shrouds 110 relative to the turntable 108 provides that the front edges 206 of the shrouds 110 remain facing the measurement module 116.
  • the surface area of the shrouds 110 orthogonal to the incident radio waves 118 tends to be minimised.
  • radar return from the shrouds 110 tends to be minimised.
  • the radar cross section of the aircraft 102 tends to be relatively large compared to the radar cross section of the aircraft mounting structure 104. This tends to increase the accuracy with which the radar cross section of the aircraft 102 is determined.
  • steps s6 to s10 are performed simultaneously or overlapping at least to some extent.
  • the turntable 108 rotates as the measurement module 116 illuminates the aircraft 102 with radio waves 118.
  • the computer determines whether or not all measurements of the aircraft 102 with the measurement module 116 in its current position and orientation on the frame 114 have been taken.
  • step s12 If at step s12, it is determined that not all measurements of the aircraft 102 with the measurement module 116 in its current position and orientation on the frame 114 have been taken, the method of Figure 7 proceeds back to step s6. On returning to step s4, the turntable 108 rotates to locate the aircraft 102 in a new orientation relative to the measurement module 116. Further measurements of the radar cross section of the aircraft 102 are then taken with the measurement module 116 in its current position and orientation on the frame 114.
  • steps s6 to s12 are iterated so as to capture a 360° radar cross section of the aircraft 102 at each position and orientation of the measurement module 116 on the frame 114.
  • step s12 it is determined that all measurements of the aircraft 102 with the measurement module 116 in its current position and orientation on the frame 114 have been taken, the method of Figure 7 proceeds to step s14.
  • the computer determines whether or not all measurements of the aircraft 102, for all desired positions and orientations of the measurement module 116 on the frame 114, have been taken.
  • step s14 If at step s14, it is determined that not all measurements of the aircraft 102, for all desired positions and orientations of the measurement module 116 on the frame 114, have been taken, the method of Figure 7 proceeds back to step s4.
  • the measurement module 116 On returning to step s4, the measurement module 116 is positioned and oriented on the frame 114 in a new desired position. For example, in a second iteration of step s4, the measurement module 116 may be located in the second position and orientation 506. Also, in a third iteration of step s4, the measurement module 116 may be located in the third position and orientation 508.
  • steps s4 to s14 are iterated so as to capture a radar cross section of the aircraft 102 for multiple angles of attack. More preferably, steps s4 to s14 are iterated so as to capture a full spherical radar cross section of the aircraft 102.
  • step s14 it is determined that all measurements of the aircraft 102, for all desired positions and orientations of the measurement module 116 on the frame 114, have been taken, the method of Figure 7 proceeds to step s16.
  • the computer processes the electronic signals corresponding to the received radar reflections received by the antennas 510 to determine a radar cross section of the aircraft 102.
  • the aircraft 102 and the aircraft support structure 104 are located in a near-field region of the antennas 510. Measuring the radar cross section of the aircraft 102 in the near-field region of the antennas 510 advantageously tends to provide that size of the measurement facility for determining aircraft radar cross sections is reduced.
  • the computer may implement a "near-field to far-field" transformation to predict far-field characteristics of the aircraft 102 from the captured near-field measurements.
  • the above described method and apparatus may be used to determine a relatively accurate measurement of the radar cross section of the aircraft.
  • the above method and apparatus is particularly useful with low observable (LO) aircraft as the radar cross section of the support structure tends to be much lower than that of the aircraft. It tends to be difficult to accurately measure the radar cross sections of LO aircraft using conventional techniques.
  • LO low observable
  • the aircraft mounting structure comprises three aircraft mounts for supporting the aircraft above the turntable.
  • the aircraft mounts comprise a cylindrical portion and a shroud.
  • the aircraft mounting structure comprises a different number of aircraft mounts.
  • one or more of the aircraft mounts has a different structure.
  • a shroud covers the entirety of a cylindrical portion.
  • one or more of the cylindrical portions is replaced by a member having a shaped other than a cylinder.
  • the shrouds are shaped as described above, for example, the shrouds have a tear-drop shaped cross section. However, in other embodiments one or more of the shrouds has a different shape.
  • the cross section of a shroud has a pointed portion that.
  • a shroud may have a diamond or triangular cross section.
  • the point portion of the cross section of the shroud is pointed towards the antennas.
  • the apparatus housed within the shrouds is as described above.
  • one or more of the shrouds houses different apparatus that is configured to counter-rotate the shroud such that the orientation of that shroud relative the antennas is maintained.
  • the measurement module comprises four antennas. However, in other embodiments, the measurement module comprises a different number of antennas.
  • the housing of the measurement module is substantially cuboidal in shaped.
  • the housing of the measurement module is a different shape.

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  • Engineering & Computer Science (AREA)
  • Computer Networks & Wireless Communication (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Radar Systems Or Details Thereof (AREA)
EP16184533.4A 2015-08-20 2016-08-17 Structure d'assemblage Withdrawn EP3133418A1 (fr)

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EP15002468.5A EP3133417A1 (fr) 2015-08-20 2015-08-20 Structure d'assemblage

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Cited By (2)

* Cited by examiner, † Cited by third party
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CN109683145A (zh) * 2018-12-14 2019-04-26 中国航空工业集团公司北京航空精密机械研究所 大尺寸边缘驱动旋转转台的台体
JPWO2021192876A1 (fr) * 2020-03-27 2021-09-30

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112720386B (zh) * 2020-12-25 2023-05-30 中国航空工业集团公司北京航空精密机械研究所 一种大尺寸多产品兼容的旋转转台

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WO2021192876A1 (fr) * 2020-03-27 2021-09-30 三菱電機株式会社 Appareil de retenue de dispositif à l'essai, et système d'essai cem
WO2021192253A1 (fr) * 2020-03-27 2021-09-30 三菱電機株式会社 Appareil de maintien de dispositif à l'essai et système de test cem
JP7062148B2 (ja) 2020-03-27 2022-05-02 三菱電機株式会社 供試機器保持装置、及びｅｍｃ試験システム

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